hi all, to studies of performance analysis on a NACA profile (lift and coefficient against AOA) is that possible to compare theoretical results, experimental results and simulation results by cosmofloworks?? can this 3 method get the same results (i have do it but i cannot get it, any suggestion?)? between how can i get the correct the theoretical results for NACA 0012 airfoil? and what is the factor that can effect lift and coefficient of NACA 0012 airfoil? anyone pls help regarding this problem....thanks a lots..